Fault estimation method for executing mechanism of integral type aero-engine

An aero-engine and actuator technology, applied in electrical testing/monitoring and other directions, can solve the problems of not considering sensors at the same time and less research results, so as to reduce the number of false triggers, improve the effect, and improve the accuracy of fault estimation.

Pending Publication Date: 2022-04-29
DALIAN UNIV OF TECH
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Problems solved by technology

However, the above-mentioned studies on fault diagnosis and fault-tolerant control of aero-engine distributed control systems and networked control systems are mainly concentrated in the field of fault detection and passive fault-tolerant control. Relatively small
The methods used in the current literature do not consider the influence of sensor measurement noise and network delay on the fault estimation results at the same time when performing fault estimation on the actuators of networked control systems such as aeroengine distributed control, which has a certain gap with the actual situation.

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  • Fault estimation method for executing mechanism of integral type aero-engine
  • Fault estimation method for executing mechanism of integral type aero-engine
  • Fault estimation method for executing mechanism of integral type aero-engine

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Embodiment Construction

[0179] The technical solution of the present invention will be further described below according to the technical solution and the accompanying drawings.

[0180] The flow chart of the fault estimation and fault-tolerant control method based on the integral event trigger mechanism is as follows: figure 1 shown. The experimental simulation verification is as follows:

[0181] This patent will use an aero-engine control system model to verify the effectiveness of the proposed fault estimation and fault-tolerant control method based on the integral event trigger mechanism. Its system matrix is ​​as follows:

[0182]

[0183] The output variable is: y=[N 2 , π T ] T , where N 2 is the high pressure rotor speed, π T is the turbine outlet drop pressure ratio. The control input variable is selected as: u=[WFM,A8] T , where WFM is the main fuel flow rate, and A8 is the area of ​​the tail nozzle. Set the sampling period as 0.1s, the upper bound of the network-induced time ...

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Abstract

The invention provides an aero-engine executing mechanism fault estimation method triggered by an integral event, and belongs to the technical field of aero-engine fault diagnosis. According to the method, an integral type event triggering mechanism is combined with a fault observer, a sensor sampling value in an event triggering judgment mechanism is changed into an average value of a period of time from an instantaneous value of a certain moment, and meanwhile, a network transmission delay effect is considered; therefore, the influence of measurement random noise on a fault estimation result can be effectively reduced, and the network communication load is reduced; and finally, verifying the effectiveness of the provided fault estimation and fault-tolerant control method based on the integral type event triggering mechanism by adopting a certain aero-engine control system model.

Description

technical field [0001] The invention belongs to the technical field of aero-engine fault diagnosis, relates to a fault diagnosis method of an aero-engine distributed control system, and in particular to a fault estimation and fault-tolerant control method of an actuator of a control system based on an integral event trigger mechanism. Background technique [0002] Distributed control is an important development direction of next-generation aero-engine control technology following FADEC (Full Authority Digital Electronic Controller). Since a large number of intelligent sensors and intelligent actuators are used in the distributed control system, drift failures are prone to occur in the harsh environment of high temperature and high vibration of the engine. Distributed control is one of the typical networked control methods, and the theoretical research on fault diagnosis and fault-tolerant control of networked control systems has made considerable progress. However, the abov...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0243G05B2219/24065
Inventor 孙希明马永康费中阳杨柳
Owner DALIAN UNIV OF TECH
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